w1 / w2 dpw-3 results - nasa 2 of 21, brodersen dpw-3, june 2006 unstructured method: tau • rans...

W1 / W2 DPW-3 Results

B. Eisfeld, J. Raddatz, P. Frohnapfel, O. BrodersenInstitute of Aerodynamics and Flow Technology

DLR38108 Braunschweig

Germany

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Unstructured Method: TAU

• RANS solver DLR TAU• Unstructured database• State-of-the-Art algorithms• 1- and 2-eq. turbulence models• Fluid-Structure coupling• Overlapping grids• Grid adaptation• Hypersonic extensions• C code and Python scripting• High performance on parallel machines• Applied in European aircraft industryand research

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Structured Method: FLOWer

• RANS solver DLR FLOWer• Structured database• Advanced turbulence and transition models

• Top-level algorithms (FV, MG, dual time)• Steady and unsteady flows• Chimera technique for moving bodies • Flow / structure coupling • Design options (inverse design, adjoint)• Fortran, portable code• Optimized for vector computers• Parallelized code

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Unstructured Grids

• Unstructured hybrid grids generated with Centaur from Centaursoft• 3 grid densities• Specification of sources• 4. grid by TAU adaptation

40

186787188794

10.1 / 9.9

Fine

403020Prismatic layers

355163352802

113182114677

4948951186

Boundarynodes

17.0 / 16.65.3 / 5.02.1 / 1.9Nodes

Fine AdapMediumCoarse

medium fine fine adapted

coarse

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TAU Results

Grid Convergence Study of CD, α=0.5o

Influence of SAE / kw-SST

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TAU Results

Grid Influence on Cp, α=0.5o

SAE model

η=0.026 η=0.551

W1

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TAU Results

Influence W1 / W2SAE / SST

η=0.026 η=0.551

W1 W2

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TAU Results

Influence of Turbulence Models SAE / kw-SST

W1 W2

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TAU Results


W1 SAE

W2 SSTW1 SST

W2 SAE

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TAU Results


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Structured Grids

• Structured grids generated by Boeing using ICEM

8.6

Fine

14.84.21.6Nodes

Very fineMediumCoarse

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FLOWer Results

Grid Convergence, SST / SSG-LLR-w, α=0.5o

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FLOWer Results

Influence of Turbulence Models SST / SSG-LLR-w

η=0.026 η=0.551

fine

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FLOWer Results


W1 W2

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FLOWer Results


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FLOWer Results

Influence of Turbulence Models SST / SSG-LLR

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Summary

• TAU SAE / kw-SST and FLOWer SST / SSG-LLR-w results showgood grid convergence behaviour

• Grid refinement improves shock resolution• TAU:

- Small upstream shift of shock location for SST vs. SAE- SAE shows higher CLmax and lower CD (vers. SST)

• FLOWer:- No significant differences of Cp for SST / SSG-LLR-w- SSG-LLR-w shows higher CLmax and lower CD (vers. SST)- SSG-LLR-w shows higher CD in linear range (α<1.5o); lower CD above

• Similar delta drag W1-W2 for both methods / turbulence models in linear range of CL-α

w1 / w2 dpw-3 results - nasa 2 of 21, brodersen dpw-3, june 2006 unstructured method: tau • rans...

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